Exploring small bodies: Nano- and microlander options derived from the Mobile Asteroid Surface Scout

Lange, Caroline; Ho, Tra‐Mi; Grimm, Christian; Grundmann, Jan Thimo; Ziach, Christian; Lichtenheldt, Roy

doi:10.1016/j.asr.2018.05.013

Cited by 21 publications

(11 citation statements)

References 67 publications

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“…Several of the technologies specifically required to realize the radar mission scenario as described above fall into this category. Other technologies such as advanced landing subsystems and new mobility concepts are also interesting and currently under development [56].…”

Section: Design Methodologies For Lander Design Reusementioning

confidence: 99%

A radar package for asteroid subsurface investigations: Implications of implementing and integration into the MASCOT nanoscale landing platform from science requirements to baseline design

et al. 2019

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Section: Design Methodologies For Lander Design Reusementioning

confidence: 99%

A radar package for asteroid subsurface investigations: Implications of implementing and integration into the MASCOT nanoscale landing platform from science requirements to baseline design

et al. 2019

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“…[82][83][84][85][86] With additional requirements for propulsion and communication in mind, we apply practical criteria based on launch accommodation [87] [88] and basic spacecraft design concepts. [3] MASCOT (9.64 kg) and its derivatives are 'nanolanders'. PHILAE (96 kg) is a 'microlander' [3] by similarity in design with highly compact microsatellites such as BIRD (92 kg) [89], TET-1 (110 kg) [90], or AsteroidFinder (~127 kg) [91].…”

Section: Motivationmentioning

confidence: 99%

“…[3] MASCOT (9.64 kg) and its derivatives are 'nanolanders'. PHILAE (96 kg) is a 'microlander' [3] by similarity in design with highly compact microsatellites such as BIRD (92 kg) [89], TET-1 (110 kg) [90], or AsteroidFinder (~127 kg) [91]. Design-driving constraints apply mainly to the launch configuration.…”

Section: Motivationmentioning

confidence: 99%

“…Any effort which intends to physically interact with asteroids requires understanding of the composition and multi-scale surface structure, or even the interior. Mobile Asteroid Surface Scout (MASCOT) landing modules and instrument carriers can provide a first access [1][2][3][4]. They integrate at the instrument level to their mothership on 'small' as well as larger interplanetary missions.…”

Section: Introductionmentioning

confidence: 99%

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Solar Sails for Planetary Defense & High-Energy Missions

Grundmann

Bauer

Borchers

et al. 2019

2019 IEEE Aerospace Conference

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20 years after the successful ground deployment test of a (20 m)² solar sail at DLR Cologne, and in the light of the upcoming U.S. NEAscout mission, we provide an overview of the progress made since in our mission and hardware design studies as well as the hardware built in the course of our solar sail technology development. We outline the most likely and most efficient routes to develop solar sails for useful missions in science and applications, based on our developed 'now-term' and near-term hardware as well as the many practical and managerial lessons learned from the DLR-ESTEC GOSSAMER Roadmap. Mission types directly applicable to planetary defense include single and Multiple NEA Rendezvous ((M)NR) for precursor, monitoring and follow-up scenarios as well as sail-propelled head-on retrograde kinetic impactors (RKI) for mitigation. Other mission types such as the Displaced L1 (DL1) space weather advance warning and monitoring or Solar Polar Orbiter (SPO) types demonstrate the capability of near-term solar sails to achieve asteroid rendezvous in any kind of orbit, from Earth-coorbital to extremely inclined and even retrograde orbits. Some of these mission types such as SPO, (M)NR and RKI include separable payloads. For one-way access to the asteroid surface, nanolanders like MASCOT are an ideal match for solar sails in micro-spacecraft format, i.e. in launch configurations compatible with ESPA and ASAP secondary payload platforms. Larger landers similar to the JAXA-DLR study of a Jupiter Trojan asteroid lander for the OKEANOS mission can shuttle from the sail to the asteroids visited and enable multiple NEA sample-return missions. The high impact velocities and re-try capability achieved by the RKI mission type on a final orbit identical to the target asteroid's but retrograde to its motion enables small spacecraft size impactors to carry sufficient kinetic energy for deflection. TABLE OF CONTENTS 1. INTRODUCTION……………………………….2 2. MOTIVATION.

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“…Log-log plot of the gravitational attraction with respect to mean diameter and bulk density of possible target objects including error margins[32] …”

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confidence: 99%

Size matters - The shell lander concept for exploring medium-size airless bodies

et al. 2020

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Once addressed as a side topic in planetary exploration, the investigation of small solar system bodies has now become one of the corner stones in the international science community in order to study the formation of the solar system and the evolution of life within. For rendezvous spacecraft, small carry-on landers have proven to be valuable assets, and to have a positive impact on the overall mission cost, by avoiding additional complexity of the main satellite and transferring the risk of close surface maneuvers entirely or at least to some extend to an independent deployable system. However, carry-on landers have been designed currently to land on very small bodies only, but medium-size class objects between diameters of 10 -50 km are of great interest as well. In this paper we classify carry-on landers with respect to their touchdown and operational strategy, evaluate the constraints of ballistic deployments for different target bodies as well as identify the niche for using simple honeycomb impact dampers compared to optional retro-propulsion systems. Further we introduce the system design of a guided Shell Lander using a generic instrument carrier attached to a single ejectable crash-pad with stabilizing capability to protect the instrument carrier from structural damage, limit internal shock loads for sensitive payloads as well as reduce the amount of bounces on the surface. Finally, we present a mission architecture for a reference case to the Martian moon Phobos as well as provide a proof of concept based on laboratory impact tests.

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Exploring small bodies: Nano- and microlander options derived from the Mobile Asteroid Surface Scout

Cited by 21 publications

References 67 publications

A radar package for asteroid subsurface investigations: Implications of implementing and integration into the MASCOT nanoscale landing platform from science requirements to baseline design

A radar package for asteroid subsurface investigations: Implications of implementing and integration into the MASCOT nanoscale landing platform from science requirements to baseline design

Solar Sails for Planetary Defense & High-Energy Missions

Size matters - The shell lander concept for exploring medium-size airless bodies

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